CN113323770B - Special device for precisely bonding throat linings of large solid rocket engine in blocks - Google Patents
Special device for precisely bonding throat linings of large solid rocket engine in blocks Download PDFInfo
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- CN113323770B CN113323770B CN202110541669.1A CN202110541669A CN113323770B CN 113323770 B CN113323770 B CN 113323770B CN 202110541669 A CN202110541669 A CN 202110541669A CN 113323770 B CN113323770 B CN 113323770B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/08—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using solid propellants
- F02K9/32—Constructional parts; Details not otherwise provided for
- F02K9/34—Casings; Combustion chambers; Liners thereof
- F02K9/346—Liners, e.g. inhibitors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
- F02K9/974—Nozzle- linings; Ablative coatings
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E30/00—Energy generation of nuclear origin
- Y02E30/30—Nuclear fission reactors
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Connection Of Plates (AREA)
- Lining Or Joining Of Plastics Or The Like (AREA)
Abstract
The invention discloses a special device for precisely bonding throat linings of a large-scale solid rocket engine in blocks, wherein the throat linings comprise M identical throat lining blocks, the M throat lining blocks group all the throat lining blocks according to a group of X blocks, the M throat lining blocks are divided into a group of F throat lining blocks, and finally the remaining Y throat lining blocks are used as adjusting throat lining blocks; the special device comprises a grouped throat lining bonding clamp and an integral throat lining bonding clamp; the throat liner block precise bonding special device consisting of the grouped throat liner bonding clamp and the integral throat liner bonding clamp can realize large-scale manufacture of the throat liner of the solid rocket engine nozzle, and solve the manufacturing problem of the large solid rocket engine; in addition, the special device has high precision of the throat insert assembled, and completely meets the requirement of product design precision.
Description
Technical Field
The invention relates to the technical field of precise bonding equipment for throat linings of solid rocket engines, in particular to a special device for partitioned precise bonding of throat linings of large solid rocket engines.
Background
In the aerospace production, relates to a method for processing and manufacturing a throat insert of a large solid rocket engine. The throat insert of the large solid rocket engine, as a key part of the large solid rocket engine (SRM), has the characteristics of large overall dimension, complex shape and structure and ablation resistance. The solid rocket engine throat insert is difficult to integrally design and integrally manufacture and form on the design of a large-size or even an oversized SRM throat insert due to the limitation of a large-size solid rocket engine throat insert preforming design, a densification process and large-size C/C throat insert hot isostatic pressing equipment. In order to meet the development requirements of large-size and super-large-size solid rocket engines, a new method is needed for the throat insert of the large-size solid rocket engine, and the throat insert is processed and manufactured by adopting a throat insert radial block forming technology. The throat liner radial block forming technology is that a large-size throat liner is divided into a plurality of block throat liners along the radial direction, a blank is prefabricated according to the block throat liners, the block throat liners are firstly processed, the block throat liners are milled into trapezoids, then the block throat liners are assembled into an integral throat liner in a bonding mode, and finally the inner and outer molded surfaces of the throat liner are turned to form the final throat liner. The throat insert blocking forming technology greatly reduces the requirements of the solid rocket engine throat insert preforming design, the densification process and the throat insert hot isostatic pressing equipment, and the SRM throat insert is realized on the large-size and oversized design.
The throat insert is a key ablation part of the SRM spray pipe, and is required to bear mechanical scouring, chemical corrosion and thermal shock of high-temperature, high-pressure and high-speed gas. When the throat insert is divided into radial blocks, the method is equivalent to artificially manufacturing a plurality of gaps in the throat insert, and the method is a great challenge for the throat insert with an extremely severe working environment. Therefore, bonding assembly gaps among all the single throat linings of the blocked throat linings are required to be as small as possible, and the gaps among the throat linings are filled uniformly and reliably by using adhesives. The assembly and machining precision of the large-sized blocking throat insert directly influences the flight performance of the aircraft.
General large throat insert inner diameter
Left and right, outer diameter
The overall height is about 900mm, the throat linings are uniformly divided into 70-80 blocked throat linings along the radial direction, and the gap between the blocked throat linings is required to be 0-0.1 mm during the assembly of the throat linings. The block throat linings have large bonding area and large number, so that the gap value of the bonding surfaces of all the block throat linings is ensured, and high requirements are provided for processing the block throat linings and precisely bonding and assembling the throat linings. When the blocked throat insert is processed, the flatness error and the angle error of the bonding surface can generate larger error accumulation in the throat insert assembling process, the gap control of the bonding surface of the blocked throat insert is directly influenced, the final integral assembling and forming of the throat insert are greatly difficult, and the large-scale throat insert is large in sizeThe throat insert is divided into blocks and precisely adhered and assembled, so that a plurality of problems are caused.
Disclosure of Invention
The invention aims to provide a special device which can ensure the bonding assembly precision of throat linings and can reduce the integral bonding difficulty of the blocked throat linings of a large solid rocket engine aiming at the defects of the existing evaluation method.
In order to realize the purpose, the throat insert special device for precisely bonding the throat inserts of the large solid rocket engine in blocks comprises M identical throat insert blocks, wherein the M throat insert blocks group all the throat insert blocks according to X throat insert blocks, and divide the throat insert blocks into F groups of throat insert blocks, and finally the remaining Y throat insert blocks are used as adjusting throat insert blocks; the special device comprises a grouped throat lining bonding clamp and an integral throat lining bonding clamp;
the grouped throat lining bonding clamp comprises a grouped bonding clamp body formed by enclosing a base, side plates and a pressing plate, a wedge block penetrating through the top of the pressing plate until the wedge block is inserted into a cavity of the grouped bonding clamp body, a locking screw used for locking the side plates and the wedge block and a tensioning screw rod, wherein the bottom end of the tensioning screw rod is inserted from the top of the wedge block until the bottom end of the tensioning screw rod is fixed with the base, and the head of the tensioning screw rod exposed outside the wedge block is locked through a nut.
Furthermore, the whole throat lining bonding clamp comprises a mandrel, a lower positioning ring sleeved at the bottom of the outer edge of the mandrel, an upper positioning ring pressed on the top of the mandrel, an upper pressing plate pressed on the top surface of the throat lining and the top surface of the positioning ring, and a flexible binding belt used for fixing the throat lining.
Furthermore, the inclination angle of the surface, attached to the throat lining blocks, of the wedge-shaped block is alpha/2, the inclination angle of the surface, attached to the wedge-shaped block, of the side plate is alpha/2, and alpha is the included angle of two bonding surfaces of each throat lining block.
Furthermore, an arc boss is arranged in the middle of the bottom surface of the base, and the arc surface of the arc boss is the same as the positioning reference arc surface of the small end surface of the throat lining block.
Furthermore, two ends of the arc boss and two baffles of the base form limiting grooves for limiting the side plates respectively.
Furthermore, a through hole is formed in the middle of the bottom of the base.
Further, the mandrel comprises a cylindrical mandrel body and a bottom ring arranged at the bottom of the cylindrical mandrel body; the lower positioning ring comprises a lower transverse positioning ring and a lower vertical positioning ring, the lower transverse positioning ring is fixed on the upper surface of the bottom ring, and the lower vertical positioning ring is attached to the outer circular surface of the cylindrical mandrel body; the upper positioning ring comprises an upper transverse positioning ring and an upper vertical positioning ring, the upper transverse positioning ring is pressed on the top surface of the cylindrical mandrel body, and the upper vertical positioning ring is attached to the outer circular surface of the cylindrical mandrel body; the bottom surface of the extending section of the upper pressure plate is locked on the upper surface of the upper transverse positioning ring through a bolt, the bottom surface of the upper pressure plate is pressed on the top surface of the throat insert, and the bottom surface of the throat insert abuts against the upper surface of the lower transverse positioning ring.
Furthermore, the outer arc surfaces of the upper vertical positioning ring and the lower vertical positioning ring are the same as the positioning reference arc surface of the throat filler block.
Furthermore, the fit clearance between the inner hole surface of the upper positioning ring and the outer circle surface of the mandrel and the fit clearance between the inner hole surface of the lower positioning ring and the outer circle surface of the mandrel are not more than 0.1, and the coaxiality is not more than 0.1.
Furthermore, a threaded through hole for demolding is formed in the bottom ring of the mandrel.
Compared with the prior art, the invention has the following advantages: the throat lining block precise bonding special device composed of the grouped throat lining bonding clamp and the integral throat lining bonding clamp can realize large-scale manufacture of the throat lining of the solid rocket engine jet pipe and solve the manufacturing problem of the large solid rocket engine; in addition, the special device has high precision of the throat insert assembled, and completely meets the requirement of product design precision.
Drawings
FIG. 1 is a schematic structural view of a grouped throat insert bonding jig according to the present invention;
FIG. 2 is a schematic view of the base structure of FIG. 1;
FIG. 3 is a schematic structural view of the bonding fixture for the integral throat insert of the present invention.
Wherein: the fixture comprises a throat filler block 1, a pressure plate 2, a tensioning screw rod 3, a wedge block 4, a locking screw 5, a side plate 6, a base 7, an upper pressure plate 8 (wherein: an extension section 8.1), an upper positioning ring 9 (wherein: an upper transverse positioning ring 9.1 and an upper vertical positioning ring 9.2), a mandrel 10 (wherein: a bottom ring 10.1, a cylindrical mandrel body 10.2 and a threaded through hole 10.3), a lower positioning ring 11 (wherein: a lower vertical positioning ring 11.1 and a lower transverse positioning ring 11.2), a flexible binding band 12, a nut 13, an arc boss 14, a limiting groove 15 and a through hole 16.
Detailed Description
The invention will be more clearly understood from the following detailed description of the invention taken in conjunction with the accompanying drawings and specific examples, which are not to be construed as limiting the invention.
The throat liner comprises M identical throat liner blocks 1, wherein the M throat liner blocks 1 are used for grouping all throat liner blocks according to X groups and are divided into F groups of throat liner blocks, the remaining Y throat liner blocks are used as adjusting throat liner blocks, the section of each throat liner block 1 in the length direction is in a fan shape, the included angle between two bonding surfaces of each throat liner block 1 is alpha, and the small end surface of each throat liner block in the length direction is provided with a positioning reference arc surface.
The throat insert is specifically partitioned into the following formulas:
M/X＝F+Y
M·α＝360°
m is the total number of throat insert blocks contained in the integral throat insert;
x is the number of throat linings contained in each group of throat linings, and 1-10 are selected;
f is the number of groups which are finally divided by the whole throat insert, and 2-M is selected;
y is the number of the remaining throat insert blocks after the throat inserts are grouped, and 0-4 is selected;
if Y is equal to 0, taking one group of throat pads in the F group as the adjusting throat pad 3;
the special device comprises a grouping throat lining bonding clamp and an integral throat lining bonding clamp. The grouped throat lining bonding clamp is used for bonding F-group throat lining blocks, and comprises a grouped bonding clamp body formed by enclosing a base 7, a side plate 6 and a pressing plate 2, a wedge block 4 penetrating from the top of the pressing plate 2 until being inserted into a cavity of the grouped bonding clamp body, a locking screw 5 and a tensioning screw 3, wherein the locking screw 5 is used for locking the side plate 6 and the wedge block 4, the outer side surface of the wedge block 4 is attached to the inner surface of the side plate 6, the bottom end of the tensioning screw 3 is inserted from the top of the wedge block 4 until being fixed with the base 7, and the head of the tensioning screw 3 exposed outside the wedge block 4 is locked through a nut 13.
The inclination angle of the surface of the wedge block 4 jointed with the throat insert block 1 is alpha/2, and the inclination angle of the surface of the side plate 6 jointed with the wedge block 4 is alpha/2. The middle part of the bottom surface of the base 7 is provided with an arc boss 14, and the arc surface of the arc boss 14 is the same as the positioning reference arc surface of the small end surface of the throat insert 1; two ends of the arc boss 14 and two baffles of the base 7 form a limiting groove 15 for limiting the side plate respectively. A through hole 16 is provided in the middle of the bottom of the base 7 for measuring the clearance of the bonding surface of the throat pad 1, as shown in fig. 2.
The throat lining blocks in each group of grouped throat lining blocks are sequentially placed in the grouped throat lining bonding fixture, then the pressing plate 2 penetrates through the wedge block 4 to be tightly pressed on the large end face of the throat lining block 1 to prevent the throat lining blocks from moving radially, the nut at the head of the adjusting tensioning screw 3 wedges the throat lining blocks 1 by means of the wedge block 4 to enable the throat lining blocks 1 to generate extrusion force, so that the gap between the throat lining blocks is roughly adjusted, and meanwhile, the gap requirements of the bonding surfaces of the throat lining blocks 1 are finely adjusted by the upper and lower rows of tightening screws 5 of the side plate 6.
The integral throat lining bonding clamp is used for integrally bonding a throat lining body, and comprises a mandrel 10, a lower positioning ring 11 sleeved at the bottom of the outer edge of the mandrel 10, an upper positioning ring 9 pressed at the top of the mandrel 10, an upper pressure plate 8 pressed on the top surfaces of the throat lining and the positioning ring 9, and a flexible binding belt 12 used for fixing the throat lining, as shown in figure 3.
The mandrel 10 comprises a cylindrical mandrel body 10.2 and a bottom ring 10.1 arranged at the bottom of the cylindrical mandrel body 10.2, and the bottom surface of the bottom ring 10.1 is flush with the bottom end surface of the cylindrical mandrel body; the lower positioning ring 11 comprises a lower transverse positioning ring 11.2 and a lower vertical positioning ring 11.1, the lower transverse positioning ring 11.2 is fixed on the upper surface of the bottom ring 10.1, and the lower vertical positioning ring 11.1 is attached to the outer circular surface of the cylindrical mandrel body 10.2; similarly, the upper positioning ring 9 comprises an upper transverse positioning ring 9.1 and an upper vertical positioning ring 9.2, the upper transverse positioning ring is pressed 9.1 on the top surface of the cylindrical mandrel body 10.2, and the upper vertical positioning ring 9.2 is attached to the outer circular surface of the cylindrical mandrel body 10.2; the bottom surface of the extension section 8.1 of the upper pressure plate 8 is locked on the upper surface of the upper transverse positioning ring 9.1 through bolts, the bottom surface of the upper pressure plate 8 is pressed on the top surface of the throat insert, and the bottom surface of the throat insert is abutted on the upper surface of the lower transverse positioning ring 11.2.
The outer arc surfaces of the upper vertical positioning ring 9.2 and the lower vertical positioning ring 11.1 are the same as the positioning reference arc surface of the throat filler block 1, the fit clearance between the inner hole surface of the upper positioning ring 9 and the inner hole surface of the lower positioning ring 11 and the outer arc surface of the mandrel 10 is not more than 0.1, and the coaxiality is not more than 0.1, so that the upper positioning ring 9 and the lower positioning ring 11 can be detached from the mandrel 10.
When the whole throat linings are bonded, the upper outer circle and the lower outer circle of the whole throat linings are hooped tightly by the flexible binding bands 12, the radial positions of the adjustable throat lining blocks are adjusted by the flexible binding bands 12, and gaps of bonding surfaces of the grouped throat linings are adjusted by the aid of the tensile force of the flexible binding bands.
In addition, a threaded through hole 10.3 is formed in a bottom ring 10.1 of the mandrel 10, and during demolding, an ejection screw is mounted through the threaded through hole 10.3 in the bottom ring of the mandrel 10 to eject the lower positioning plate 11, and the throat liner is lifted from the mandrel 10 and demolded, so that the lower positioning ring 11 also has a supporting plate function and is used for lifting and demolding the throat liner from the mandrel.
Claims (6)
1. A throat liner of a large-scale solid rocket engine is accurate to glue the specialized device separately, the throat liner includes M identical throat filler blocks (1), M throat filler blocks group all throat liner blocks according to X one group, divide into F group throat filler blocks, Y throat filler blocks left at last are regarded as and adjusted the throat filler block; the method is characterized in that: the special device comprises a grouped throat lining bonding clamp and an integral throat lining bonding clamp;
the grouped throat lining bonding clamp comprises a grouped bonding clamp body formed by enclosing a base (7), side plates (6) and a pressing plate (2), a wedge-shaped block (4) penetrating from the top of the pressing plate (2) until being inserted into a cavity of the grouped bonding clamp body, a locking screw (5) and a tensioning screw (3) which are respectively used for locking the side plates (6) and the wedge-shaped block (4), wherein the bottom end of the tensioning screw (3) is inserted from the top of the wedge-shaped block (4) until being fixed with the base (7), and the head of the tensioning screw (3) exposed outside the wedge-shaped block (4) is locked through a nut (13);
the integral throat insert bonding clamp comprises a mandrel (10), a lower positioning ring (11) sleeved at the bottom of the outer edge of the mandrel (10), an upper positioning ring (9) pressed on the top of the mandrel (10), an upper pressing plate (8) pressed on the top surfaces of a throat insert and the upper positioning ring (9), and a flexible binding belt (12) used for fixing the throat insert; the mandrel (10) comprises a cylindrical mandrel body (10.2) and a bottom ring (10.1) arranged at the bottom of the cylindrical mandrel body (10.2); the lower transverse positioning ring (11.2) is fixed on the upper surface of the bottom ring (10.1), and the lower vertical positioning ring (11.1) is attached to the outer circular surface of the cylindrical mandrel body (10.2); the upper positioning ring (9) comprises an upper transverse positioning ring (9.1) and an upper vertical positioning ring (9.2), the upper transverse positioning ring (9.1) is pressed on the top surface of the cylindrical mandrel body (10.2), and the upper vertical positioning ring (9.2) is attached to the outer circular surface of the cylindrical mandrel body (10.2); the bottom surface of the extension section (8.1) of the upper pressure plate (8) is locked on the upper surface of the upper transverse positioning ring (9.1) through a bolt; the lower positioning ring (11) comprises a lower transverse positioning ring (11.2) and a lower vertical positioning ring (11.1), the bottom surface of the upper pressure plate (8) is pressed on the top surface of the throat insert, and the bottom surface of the throat insert abuts against the upper surface of the lower transverse positioning ring (11.2); the outer arc surfaces of the upper vertical positioning ring (9.2) and the lower vertical positioning ring (11.1) are the same as the positioning reference arc surface of the throat filler block (1);
the outer side surface of the wedge-shaped block (4) is attached to the inner surface of the side plate (6), and the inner side surface of the wedge-shaped block (4) is attached to the outer side surface of the throat filler block (1).
2. The special device for the block precise bonding of the throat insert of the large-scale solid rocket engine according to claim 1, which is characterized in that: the middle part of the bottom surface of the base (7) is provided with an arc boss (14), and the arc surface of the arc boss (14) is the same as the positioning reference arc surface of the small end surface of the throat filler block (1).
3. The special device for the block precise bonding of the throat insert of the large-scale solid rocket engine according to claim 2, wherein: and two ends of the arc boss (14) and the two baffles of the base (7) form limiting grooves (15) for limiting the side plates respectively.
4. The special device for the block precise bonding of the throat insert of the large-scale solid rocket engine according to claim 1, which is characterized in that: the middle of the bottom of the base (7) is provided with a through hole (16).
5. The special device for the block precise bonding of the throat insert of the large-scale solid rocket engine according to claim 1, which is characterized in that: the fit clearance between the inner hole surface of the upper positioning ring (9) and the inner hole surface of the lower positioning ring (11) and the outer circular surface of the mandrel (10) is not more than 0.1, and the coaxiality is not more than 0.1.
6. The special device for the block precise bonding of the throat insert of the large-scale solid rocket engine according to claim 1, which is characterized in that: a bottom ring (10.1) of the mandrel (10) is provided with a threaded through hole (10.3) for demolding.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110541669.1A CN113323770B (en) | 2021-05-18 | 2021-05-18 | Special device for precisely bonding throat linings of large solid rocket engine in blocks |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110541669.1A CN113323770B (en) | 2021-05-18 | 2021-05-18 | Special device for precisely bonding throat linings of large solid rocket engine in blocks |
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| CN113323770A CN113323770A (en) | 2021-08-31 |
| CN113323770B true CN113323770B (en) | 2022-08-09 |
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Families Citing this family (1)
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| CN113799031A (en) * | 2021-10-15 | 2021-12-17 | 晋西工业集团有限责任公司 | Combined clamping device for bonding shell lining |
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| US6779458B1 (en) * | 2003-11-07 | 2004-08-24 | Chung-Shan Institute Of Science & Technology | Method and apparatus for installing aft insulation in rocket motor case |
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| CN107718576A (en) * | 2017-09-14 | 2018-02-23 | 湖北三江航天江北机械工程有限公司 | The ring piecemeal assembly method of insert nozzle larynx lining |
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2021
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2877504A (en) * | 1954-08-02 | 1959-03-17 | Phillips Petroleum Co | Method of bonding propellant grain to metal case |
| US3943208A (en) * | 1971-06-02 | 1976-03-09 | Her Majesty The Queen In Right Of Canada As Represented By The Minister Of National Defense | Method for binding solid propellant to rocket motor case |
| US6779458B1 (en) * | 2003-11-07 | 2004-08-24 | Chung-Shan Institute Of Science & Technology | Method and apparatus for installing aft insulation in rocket motor case |
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| CN113323770A (en) | 2021-08-31 |
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